Janus – A New Approach to Air Combat Pilot Training

[1] EDIDP (European Defence Industrial Development Programme), EDIDP-ACC-CJTP-2019, Call identifier: Call EDIDP-ACC-2019, Brussels, European Commission; Search in Google Scholar

[2] http://aviationweek.com/defense/multimission-concept-lightweight-advanced-trainers, accessed May 11 2016; Search in Google Scholar

[3] APP Aircraft Performance Program (trade mark) developed and source code owned (not released) by ALR. Commercial product. ALR Zurich, Switzerland; Search in Google Scholar

[4] Hillaker H., YF-16 Design Concept and Philosophy, Paper presented at 23 Israel Annual Conference on Aviation and Astronautics, 11-12 Feb. 1981, Edited by Univ.Michigan, April 1991. Search in Google Scholar

[5] Whitford R., Design for Air Combat, Jane’s Publishing Company Ltd, London 1987. Search in Google Scholar

[6] Asselin M., An Introduction to Aircraft Performance, AIAA Inc., Reston VA, 1997.10.2514/4.861529 Search in Google Scholar

[7] Orlik-Rückemann K.J., Aerodynamics of Manoeuvring Aircraft, Canadian Aeronautics and Space Journal, Vol.38, No.3, Sept.1992, pp.106-115. Search in Google Scholar

[8] Herbst W.B., Supermanoeuvrability, Proc. of AFOSR-FJSRL Workshop on Unsteady Separated Flow. Colorado Springs, August 1983. Search in Google Scholar

[9] Robinson B.A., Barnett R.M., Agrawal S., Simple Numerical Criterion for Vortex Breakdown, AIAA Journal, Vol.32, No.1, 1994, pp.116-122.10.2514/3.11958 Search in Google Scholar

[10] Orlik-Rückemann K.J., Aerodynamic Coupling between Lateral and Longitudinal Degrees of Freedom, AIAA Journal, Vol.12, No.12, 1977, pp.1792-1799.10.2514/3.60843 Search in Google Scholar

[11] Orlik-Rückemann K.J., Dynamic Stability Testing of Aircraft - Needs Versus Capabilities, Prog.Aerospace Sci., Vol.16, No.4, 1975, pp.431-447.10.1016/0376-0421(75)90005-6 Search in Google Scholar

[12] Orlik-Rückemann K.J., Aerodynamic Aspects of Aircraft Dynamics at High Angles of Attack, Jour.of Aircraft, Vol.20, No.9, Sept.1983, pp.737-752.10.2514/3.44938 Search in Google Scholar

[13] Rom J., High Angle of Attack Aeodynamics, Springer-Verlag, Berlin 1992.10.1007/978-1-4612-2824-0 Search in Google Scholar

[14] Gordnier R.E., Computation of Vortex Breakdown on a Rolling Delta Wing, Jour.of Aircraft, Vol.32, No.3, pp.686-688.10.2514/3.46777 Search in Google Scholar

[15] Gordnier R., Computation of Delta Wing Roll Maneuvers, Jour.of Aircraft, Vol.32, No.3, May-June 1995, pp.486-492.10.2514/3.46746 Search in Google Scholar

[16] Kandil O., Chuang H., Computation of Vortex-Dominated Flow for a Delta Wing Undergoing Pitching Oscillation, Jour. of Aircraft, Vol.28, No.9, Sept.1990, pp.1589-1595.10.2514/3.25257 Search in Google Scholar

[17] Kandil O., Chuang H., Influence of Numerical Dissipation on Computational Euler Equations for Vortex-Dominated Flows, AIAA Journal, Vol.25, Nov.1987, pp.1426-1434.10.2514/3.9800 Search in Google Scholar

[18] Kandil O., Recent Advances in Multidisciplinary Aeronautical Problems of Fluid/Structures/Dynamics Interaction, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw 1997, Part I, pp. 15-34. Search in Google Scholar

[19] Menzies M., Kandil O., Natural Rolling Responces of a Delta Wing in Transonic and Subsonic Flows, AIAA Atmospheric Flight Mechanics Conference, AIAA-96-3391, pp.246-254, San Diego 1996.10.2514/6.1996-3391 Search in Google Scholar

[20] Kandil O., Kandil H., S.Massey, Simulation of Tail Buffet Using Delta Wing Vertical Tail Configuration, AIAA Atmospheric Flight Mechanics Conference, AIAA-93-3688, pp.566-577, Monterery 1993.10.2514/6.1993-3688 Search in Google Scholar

[21] Kandil O., Sheta E., Massey S., Buffet Responses of a Vertical Tail in Vortex Breakdown Flows, AIAA Atmospheric Flight Mechanics Conference, AIAA-95-3464, pp.345-360, Baltimore 1995.10.2514/6.1995-3464 Search in Google Scholar

[22] Kandil O., Massey S., Sheta E., Aerostructural Vortical Flow Interactions with Applications to F/A-18 and F-117 Tail Buffet, High-Angle-of-Attack Technology Conference, NASA Langley Research Center, Hampton, VA, Sept.1996, (20 p.). Search in Google Scholar

[23] Hsu C., Liu C., Numerical Study of Vortex-Dominated Flows for Wings at High Incidence and Sideslip, Jour. of Aircraft, Vol.29, No.3, May-June 1992, pp.396-403.10.2514/3.46175 Search in Google Scholar

[24] Lopez J., Axisymmetric Vortex Breakdown, J.Fluid Mech., (1990), Vol.221, Part 1. Confined Swirling Flow: pp.533-552, Part 2. Physical Mechanisms: pp.553-576. Search in Google Scholar

[25] Strohmeyer D., Orlowski M., Longo J., Hummel D., Bergmann A., An Analysis of Vortex Breakdown Predicted by the Euler Equations, ICAS Proceedings, 96-1.6.3., pp.1189-1200, Sorento 1996. Search in Google Scholar

[26] Boffadossi M., Calculation of Vortex Breakdown over „delta” Wing by a Vortex-Lattice Method, ICAS Proc. of 20^th Congress, Sorrento, Sept.1996, pp.1201-1210. Search in Google Scholar

[27] Robinson B.A., Barnett R.M., Agrawal S., Simple Numerical Criterion for Vortex Breakdown, AIAA Journal, Vol.32, No.1, 1994, pp.116-122.10.2514/3.11958 Search in Google Scholar

[28] Gursul I., Criteria for Location of Vortex Breakdown over Delta Wings, Aeronautical Journal, May 1995, pp.194-196.10.2514/6.1994-536 Search in Google Scholar

[29] Luckring J., Aerodynamics of Strake-Wing Interaction, Journ. of Aircraft, Vol.16, No.11, Nov.1979, pp.756-762.10.2514/3.58600 Search in Google Scholar

[30] Polhamus E.C., A Concept of the Vortex Lift of Sharp-Edge Delta Wing based on a Leading-Edge-Suction Analogy, NASA TN D-3767, 1966. Search in Google Scholar

[31] Polhamus E.C., Predictions of Vortex-Lift Characterisctics by a Leading-Edge Suction Analogy, Journ.of Aircraft, Vol.8, No.4, April 1971, pp.193-199.10.2514/3.44254 Search in Google Scholar

[32] Vizel E., Gontchar A., Investigations of Aerodynamic Characteristics of Part-Scale Aircraft Model of Moderate Wing Sweep Angle and the Structure of Vortices versus the LEX’s Form-in Plane and its Parameters, (In Russian), Journal - Technika Vojennogo Flota (TBФ), No.1-2, 1994, pp.52-58. Search in Google Scholar

[33] Tu E.L., Vortex-Wing Interaction of a Close-Coupled Canard Configuration, Jour. of Aircraft, Vol.31, No.2, 1994, pp.314-321.10.2514/3.46489 Search in Google Scholar

[34] Gordnier R., Visbal M., Unsteady Vortex Structure over a „delta” Wing, Jour. of Aircraft, Vol.31, No.1, Jan.-Feb. 1994, pp.243-248.10.2514/3.46480 Search in Google Scholar

[35] Wood R., Miller D., Assessment of Preliminary Prediction Techniques for Wing Leading-Edge Vortex Flows at Supersonic Speeds, Jour.of Aircraft, Vol.22, No.6, June 1985, pp.473-485.10.2514/3.45151 Search in Google Scholar

[36] Delery J., Aspects of Vortex Breakdown, Prog. Aerospace Sci., Vol.30, pp.1-59, 1994.10.1016/0376-0421(94)90002-7 Search in Google Scholar

[37] Ekaterinaris J.A., Schiff L.B., Navier-Stokes Solutions for an Oscillating Double-delta Wing, J. Of Aircraft, 32, 2, 1995, pp.228-234.10.2514/3.46708 Search in Google Scholar

[38] Cornelius K.C., Analysis of Vortex Bursting Utilizing Three-Dimensional Laser Measurements, Journ. of Aircraft, Vol.32, No.2, March-April 1995, pp.297-306.10.2514/3.46716 Search in Google Scholar

[39] Hoeijmakers H., Computational Vortex Flow Aerodynamics, AGARD CP-342, 1983, No. 18, pp.18.1-18.35. Search in Google Scholar

[40] Hitzel S.M., Schmidt W., Slender Wings with Leading-Edge Vortex Separation - a Challenge for Panel-Methods and Euler-Codes, AIAA Paper 83-0262, 1983.10.2514/6.1983-562 Search in Google Scholar

[41] Ericson L., Challenges in High-Alpha Vehicle Dynamics, Prog. Aerospace Sci., Vol.31, pp.291-334, 1995.10.1016/0376-0421(95)00002-G Search in Google Scholar

[42] Ericson L., Pitch Rate Effects on „delta” Wing Vortex Breakdown, Journal of Aircraft, Vol.33, No.3, May-June 1996, pp.639-642.10.2514/3.46998 Search in Google Scholar

[43] Ericson L., Delta Wing Vortex Breakdown Dynamics, AIAA Paper 95-0367, Jan.1995.10.2514/6.1995-367 Search in Google Scholar

[44] Khrabrov A., Kolinko K., Experimental Investigations of the High Aspect Ratio Wing Unsteady Aerodynamics at Stall Regimes and its Mathematical Modeling, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp. 195-200. Search in Google Scholar

[45] Khrabrov A., Miatov O., Experimental and Theoretical Investigations of Delta Wing High Angles of Attack Unsteady Aerodynamics, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp. 201-206. Search in Google Scholar

[46] Greenwell D., Wood N., Some Observations on the Dynamic Response to Wing Motion of the Vortex Burst Phenomenon, Aeronautical Journal, Feb.1994, pp.49-59.10.1017/S000192400005020X Search in Google Scholar

[47] Mabey D., Unstedy Vortex Flow Phenomena on „delta” Wings at High Angles of Incidence, ICAS Proceedings, 96-1.6.1., pp.1167-1176, Sorento 1996. Search in Google Scholar

[48] Alcorn C., Croom M., Francis M., Ross H., The X-31 Aircraft: Advances in Aircraft Agility and Performance, Prog. Aerospace Sci., Vol.32, pp.377-413, 1996.10.1016/0376-0421(95)00006-2 Search in Google Scholar

[49] Dzelnin Yu., Aircraft Stability and Maneuverability During Dynamic Departure at High Angles of Attack (In Russian), Journal - Technika Vojennogo Flota (TBФ), No 1-2, 1994, pp.59-66. Search in Google Scholar

[50] J.Rom, High Angle of Attack Aerodynamics - the State of Art and Future Challenges, Proceedings of Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp.41-54. Search in Google Scholar

[51] Goraj Z., New Directions of Research in Aeronautical Engineering - Breaking the Barriers, Journal of Theoretical and Applied Mechanics, 4, 35, 1997, pp.781-812. Search in Google Scholar

[52] Pamadi B.N., Performance, Stability, Dynamics, and Control of Airplanes, AIAA Education Series, 1998. Search in Google Scholar

[53] Payne F.M., Nelson R.C., An Experimental Study of Vortex Breakdown on a Delta Wing, NASA CP-2416, 1992. Search in Google Scholar

[54] Skow A.M., Titriga A.Jr., Moore W.A., Forebody-Wing Vortex Interactions and their Influence on Departure and Spin Resistance, CP-247, AGARD, paper 6, 1979. Search in Google Scholar

[55] NASA Report TP 2011, Exploratory Study of the Effects of Wing-Leading Edge Modifications on the Stall/Spin Behaviour of a Light General Aviation Airplane, Washington DC, 1982. Search in Google Scholar

[56] DiCarlo D.J., Glover K.E., Stewart E.C., Stough H.P., Discontinuous Wing Leading Edge to Enhance Spin Resistance, Journal of Aircraft, Vol.22, 4, 1985, pp.283-288.10.2514/3.45121 Search in Google Scholar

[57] Ghmman A.H., Goraj Z., Review On The Influence Of High Angle Of Attack Aerodynamics On Aircraft Dynamic Stability, Jour.Theor. Appl.Mech., 3, 33, 1995, pp.667-686. Search in Google Scholar

[58] Ross A.J., Investigation of Nonlinear Motion Experienced on a Slender-Wing Research Aircraft, Journal of Aircraft, Vol.9, 1972, pp.625-631.10.2514/3.59050 Search in Google Scholar

[59] Ericson L.E., Wing Rock Generated by Forebody Vortices, AIAA Paper 87-0268, 1987.10.2514/6.1987-268 Search in Google Scholar

[60] Murri D., Shah G., DiCarlo D., Actuated Forebody Strake Controls for the F 18 High Alpha Research Vehicle, Journal of Aircraft, Vol.32, 3, May-June 1995, pp.555-562.10.2514/3.46755 Search in Google Scholar

[61] Ng T.T., Suarez C.J., Kramer B.R., Ong L.Y., Ayers B., Malcolm G.N., Forebody Vortex Control for Wing Rock Supression, Journal of Aircraft, Vol.31, 2, 1994, pp.298-305.10.2514/3.46487 Search in Google Scholar

[62] Murri D.G., Nguyen L.T., Grafton S.B., Wind-Tunnel Free-Flight Investigation of a Model of a Forward-Swept-Wing Fighter Configuration, NASA TP 2230, Feb.1984. Search in Google Scholar

[63] Hsu C.H., Lan C.E. Theory of Wing Rock, J.of Aircraft 1985, Vol.22, No.10, pp.920-924.10.2514/3.45225 Search in Google Scholar

[64] Weissman R., Status of Design Criteria for Predicting Departure Characteristics and Spin Susceptibility, Journal of Aircraft, Vol.12, 12, 1975, pp.989-993.10.2514/3.59904 Search in Google Scholar

[65] Hillaker H., YF-16 Design Concept and Philosophy, Paper presented at 23 Israel Annual Conference on Aviation and Astronautics, 11-12 Feb. 1981, Edited by Univ.Michigan, April 1991. Search in Google Scholar

[66] Bitten R., Operational Benefits of Thrust Vectoring (TVC), NASA CP-3149, Part 2, Vol.I, 1990, pp.587-601. Search in Google Scholar

[67] Grafton S.B., Libbey Ch.E., Dynamic Stability Derivatives of a Twin-Jet Fighter model for Angles of Attack from -10o to 110o, NASA TN D-6091, Washington Jan.1971. Search in Google Scholar

[68] Busemann A., Aerodynamic Forces at Supersonic Speeds, Luftfahrtforschung, Vol.12, No 6, Oct.3, 1935. Search in Google Scholar

[69] Wilson H.A., Lovell J.C., Full Scale Investigation of the Maximum Lift Flow Characteristics on an Airplane Having Approximately Triangular Planform, NACA RM L6K20, Nov.1946. Search in Google Scholar

[70] Peckham D.H., Atkinson S.A., Preliminary Results of Low Speed Wind Tunnel Test on a Gothic Wing of Aspect Ratio 1.0, Aeronautical Research Council, CP 508, April 1957. Search in Google Scholar

[71] Werle H., Sur l’eclatement des tourbillions d’apex d’une aile delta aux faibles vitesses, La Recherche Aeronautique, No.74, Jan/Feb 1960. Search in Google Scholar

[72] Lambourne N.C., Bryer D.W., The Bursting of Leading Edge Vortices – Some Observationa and Discussion of the Phenomenon, Report and Memoranda No.3282, Aeronautical Research Council, April 1961. Search in Google Scholar

[73] Squire H.B., Analysis of the Vortex Breakdown Phenomenon, Part I, Imperial College of Science and Technology, Aeronautics Department, Report No.102, August 1960. Search in Google Scholar

[74] Taylor S.L. et.al., Experimental and Computational Study of the Subsonic Flow About a 75° Swept Delta Wing, AIAA Paper 87-2425. Search in Google Scholar

[75] Gordnier R.E., Visbal M.R., Numerical Simulation of the Unsteady Vortex Structure Over a Delta Wing, AIAA Paper 91-1811. Search in Google Scholar

[76] Webster W.P., Shang J.S., Numerical Simulation of Vortex Breakdown Over a Delta Wing, AIAA Paper 91-1814. Search in Google Scholar

[77] Kandil O.A., Kandil H.A., Liu C.H., Shock Vortex Interaction Over a 65° Delta Wing in Transonic Flow, AIAA Paper 93-2973. Search in Google Scholar

[78] Aerodynamic Staff of the National Physical Laboratory, Technical Report by the Accident Investigation Subcommittee on the Accident to the Aeroplane G AAZK at Meopham, Kent (England), on 21 July 1930, Aeronautical Research Council, Report and Memoranda No.1360, 1931. Search in Google Scholar

[79] White J.A., Hood M.J., Wing Fuselage Interference, Tail Buffeting and Air Flow About the Tail of a Low Wing Monoplane, NACA Technical Report No.482, 1934. Search in Google Scholar

[80] Abdrashitov G., Tail Buffeting, TsAGI, Moscow, Report No.395, 1935, NACA TM 1041, 1943. Search in Google Scholar

[81] Triplett W.E., Pressure Measurement on Twin Vertical Tails in Buffeting Flow, Journal of Aircraft, Vol.20, No.1, 1983, pp.920-925.10.2514/3.48193 Search in Google Scholar

[82] Ericson G.E. et.al., Experimental Investigation of the F/A 18 Vortex Flows at Subsonic Through Transonic Speeds, AIAA Paper 89 2222. Search in Google Scholar

[83] Cole S.R., Moss S.W., Doggett Jr. R.V., Some Buffet Response Characteristics of a Twin Vertical Tail Configuration, NASA TM 102749, Oct.1990. Search in Google Scholar

[84] Lee B.H.K. et.al., Wind Tunnel Investigation of Tail Buffet on the F-18 Aircraft, Paper 1, AGARD Conference Proceedings No.483, 1990.10.2514/6.1990-1432 Search in Google Scholar

[85] Washburn A.E., Jenkins L.N., Ferman M.A., Experimental Investigation of Vortex Fin Interaction, AIAA Paper 93 0050. Search in Google Scholar

[86] Rizk Y.M., Guruswamy G.P., Gee K., Numerical Investigation of Buffet on F 18 Aircraft, AIAA Paper 92-2673. Search in Google Scholar

[87] Kandil O.A., Kandil H.A., Massey S.J., Simulation of Tail Buffet Using Delta Wing Vertical Tail Configuration, AIAA 93-3688 CP, pp.566-577. Search in Google Scholar

[88] Kandil O.A., Flanagan M.W., Vertical Tail Buffet in Vortex Breakdown Flows, 5^th International Symposium on Computational Fluid Dynamics, Sendai, Japan, August 31 Sept.3, 1993. Search in Google Scholar

[89] Kandil O.A., Massey S.J., Kandil H.A., Computations of Vortex Breakdown Induced Tail Buffet Undergoing Bending and Torsional Vibrations, AIAA Paper 94-1428. Search in Google Scholar

[90] Hirsch C.: Numerical Computation of Internal and External Flows, Vol 1-2, 1988. Search in Google Scholar

[91] Beam R.M., Warming R.F., An Implicit factored Scheme for the Compressible Navier Stokes Equations, AIAA Journal, Vol.16, No.4, 1978, pp.393-402.10.2514/3.60901 Search in Google Scholar

[92] Steger J.L., Warming R.F., Flux Vector Splitting of the Inviscid Gasodynamic Equations with Application to Finite Difference Methods, NASA TM 78605, July 1979 (also Journal Of Comp.Physics, Vol.40, No.2, April 1981, pp.263-293).10.1016/0021-9991(81)90210-2 Search in Google Scholar

[93] Van Leer B., Flux Vector Splitting for the Euler Equations, ICASE Report 82-30, Sept.1982 (also Lecture Notes in Physics, Vol.170, 1982, pp.507-512).10.1007/3-540-11948-5_66 Search in Google Scholar

[94] Thomas J.L., Van Leer B., Walters R.W., Implicit Flux Schemes for the Euler Equations, AIAA Paper 85-1680. Search in Google Scholar

[95] Massey S.J., A Direct Numerical Simulation of Vortex Braekdown Induced Tail Buffet, M.Sc. Degree Thesis, Old Dominion University, May 1994, (unpublished). Search in Google Scholar

[96] Kandill O.A., Recent Advances in Multidisciplinary Aeronautical Problems of Fluids/Structures/Dynamics Interaction, Proceedings of Second International Seminar RRDPAE_1996, Edited by Z.Goraj, Warsaw 1996, pp.15-34. Search in Google Scholar

[97] Küchemann D., The aerodynamic design of aircraft. Pergamon Press, Oxford 1978. Search in Google Scholar

[98] AGARD Conference Proceedings CP 319, Combat Aircraft Manoeuvrability, Dec.1981. Search in Google Scholar

[99] Mabey D.G., Some aspecs of aircraft dynamic loads due to flow separation. Progress in Aerospace Science, No. 2, 1989.10.1016/0376-0421(89)90006-7 Search in Google Scholar

[100] Mabey D.G., An hypothesis for the prediction of flight penetration of ming buffeting from dynamic tests of a wind tunnel model. ARC CP 1171, 1971. Search in Google Scholar

[101] Kania W., Gnarowski W., Jóźwiak R., Stalewski W., Wysocki Z., Zwierchanowska B., Żółtak J., Aerodynamic Design and Wind Tunnel Tests of Advanced Attack Aircraft Cobra 2000, Proc.of the Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, Part I, Edited by Z.Goraj, Warsaw 1997, pp.169-174. Search in Google Scholar

[102] Romanowski R., Low Speed Tests of the Dorsal Intake Pressure Recovery for Cobra 2000 Aircraft, Proc.of the Second Seminar on „Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, Part II, Edited by Z.Goraj, Warsaw 1997, pp.63 -68. Search in Google Scholar

[103] Holligsworth E.H., Lohen M., Determination of F 4 Aircraft Transonic Buffet Characteristics, Jour. of Aircraft, Vol.8. No.10, October, 1971.10.2514/3.59167 Search in Google Scholar

[104] Damstrom E.K., Mayes J.F., Transonic Flight and Wind Tunnel Buffet Onset Investigation of the F 8D Aircraft, Jour. of Aircraft, Vol.8. No.4, April, 1971.10.2514/3.44266 Search in Google Scholar

[105] Herbst W., Dynamics of Air Combat, J.Aircraft, Vol.20, No.7, July 1983, pp.594-598.10.2514/3.44916 Search in Google Scholar

[106] Samoilovitch O., Aerodynamic Configurations of Contemporary and Prospective Fighters, Proc.of Second Seminar on “Recent Research and Design Progress on Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw, Nov. 1996, part II, pp.233-246. Search in Google Scholar

[107] Rom J., High Angle of Attack Aerodynamics the State of Art and Future Challenges, Proceedings of Second Seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Goraj Z., Warsaw 1997, Part I, pp.41-54. Search in Google Scholar

[108] Alcorn C., Croom M., Francis M., Ross H., The X 31 Aircraft: Advances in Aircraft Agility and Performance, Progr. Aerosp. Sc., Vol.32, pp.377-413, 1996.10.1016/0376-0421(95)00006-2 Search in Google Scholar

[109] Whitford R., Fundamentals of Fighter Design, Cycle 6 papers in Air International, 1996-97. Search in Google Scholar

[110] Delery J.M., Aspects of Vortex Breakdown, Progr. Aerosp. Sc., 30, 1994, pp.1-59.10.1016/0376-0421(94)90002-7 Search in Google Scholar

[111] Lopez J., Axisymmetric Vortex Breakdown, J.Fluid Mech., (1990), Vol.221, Part 1. Confined Swirling Flow: pp.533-552, Part 2. Physical Mechanisms: pp.553-576.10.1017/S0022112090003664 Search in Google Scholar

[112] Boffadossi M., Calculation of Vortex Breakdown over Delta Wing by a Vortex Lattice Method, ICAS Proc. of 20^th Congress, Sorrento, Sept.1996, pp.1201-1210. Search in Google Scholar

[113] Robinson B.A., Barnett R.M., Agrawal S., Simple Numerical Criterion for Vortex Breakdown, AIAA Journal, Vol.32, No.1, 1994, pp.116-122.10.2514/3.11958 Search in Google Scholar

[114] Gursul I., Criteria for Location of Vortex Breakdown over Delta Wings, Aeronautical Journal, May 1995, pp.194-196.10.2514/6.1994-536 Search in Google Scholar

[115] Luckring J., Aerodynamics of Strake Wing Interaction, Journ.of Aircraft, Vol.16, No.11, Nov.1979, pp.756-762.10.2514/3.58600 Search in Google Scholar

[116] Vizel E., Gontchar A., Investigations of Aerodynamic Characteristics of Part Scale Aircraft Model of Moderate Wing Sweep Angle and the Structure of Vortices versus the LEX’s Form in Plane and its Parameters, (In Russian), Journ. Technika Vojennogo Flota, No 1-2, 1994, pp.52-58. Search in Google Scholar

[117] Yu Dzelnin, Aircraft Stability and Maneuverability During Dynamic Departure at High Angles of Attack (In Russian), Journal - Technika Vojennogo Flota (TBФ), No 1 2, 1994, pp.59-66. Search in Google Scholar

[118] Ericsson L., Challenges in High Alpha Vehicle Dynamics, Progr. Aerosp. Sc., Vol.31, pp.291-334, 1995.10.1016/0376-0421(95)00002-G Search in Google Scholar

[119] Ericsson L., King H., Rapid Prediction of High Alpha Unsteady Aerodynamics of Slender Wing Aircraft, Journ.of Aircraft, Vol.29, No.1, Jan. Feb.1992, pp.85-92.10.2514/3.46129 Search in Google Scholar

[120] Ericsson L., Pitch Rate Effects on Delta Wing Vortex Breakdown, Vol.33, No.3, May-June 1996, pp.639-642.10.2514/3.46998 Search in Google Scholar

[121] Ericsson L., Delta Wing Vortex Breakdown Dynamics, AIAA Paper 95-0367, Jan.1995.10.2514/6.1995-367 Search in Google Scholar

[122] Khrabrov A., Kolinko K., Experimental Investigations of the High Aspect Ratio Wing Unsteady Aerodynamics at Stall Regimes and its Mathematical Modeling, Proceedings of Second Seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw 1997, Part I, pp. 195-200. Search in Google Scholar

[123] Khrabrov A., Miatov O., Experimental and Theoretical Investigations of Delta Wing High Angles of Attack Unsteady Aerodynamics, Proceedings of Second Seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education”, edited by Z.Goraj, Warsaw 1997, Part I, pp. 201-206. Search in Google Scholar

[124] Norris G., Breaking the Stall Barrier, Flight International, 11-17 Nov.1992, pp.34-37. Search in Google Scholar

[125] Ghmmam A.A., Goraj Z., A Review of the Influence of High Angle of Attack Aerodynamics on Aircraft Dynamic Stability, Jour.Ther.Appl.Mech., 3, 33, 1995, pp.667-686. Search in Google Scholar

[126] Well K.H., Faber B., Berger E., Maneuver Optimization of Aircraft Utilizing High Angles of Attack, ICAS Proceedings, 80-6.4., pp.257-264, 1980. Search in Google Scholar

[127] Manor D., Wentz Jr. W., Flow over Double-Delta Wing and Wing Body at High Alpha, Jour.of Aircraft, Vol.22, No.1, Jan.1985, pp.78-82.10.2514/3.45083 Search in Google Scholar

[128] Tu E.L., Vortex Wing Interaction of a Close Coupled Canard Configuration, Jour.of Aircraft, Vol.31, No.2, March-April 1994, pp.314-321.10.2514/3.46489 Search in Google Scholar

[129] Beyers M.E., Interpretation of Experimental High-Alfa Aerodynamics - Implications for Flight Prediction, Jour. of Aircraft, Vol.32, No.2, March April 1995, pp.247-261.10.2514/3.46710 Search in Google Scholar

[130] Beyers M., Investigation of High Manoeuvrability Flight Vehicle Dynamics, ICAS Proceedings, 80 7.2., pp.278-292, 1980. Search in Google Scholar

[131] John H., Kraus W., High Angle of Attack Characteristics of Different Fighter Configurations, AGARD-CP-247, Paper 2(15), 1979. Search in Google Scholar

[132] Rom J., High Angle of Attack Aerodynamics; Subsonic, Transonic, and Supersonic Flows, Springer Verlag, New York 1992. Week & Space Technology, Aug.8, 1994, p.54.10.1007/978-1-4612-2824-0 Search in Google Scholar

[133] Chambers J.R.,Overview of Stall/Spin Technology, AIAA Paper 80-1580, Danvers Aug.1980.10.2514/6.1980-1580 Search in Google Scholar

[134] Goraj Z., Aerodynamics For High AOA And Introduction Of Polish Aviation Study, Proceedings of The 35^th Aircraft Symposium, Tokyo 1997, pp.177-180. Search in Google Scholar

[135] Tu E.L., Effect of Canard Deflection on Close-Coupled Canard-Wing-Body Aerodynamics, Jour.of Aircraft, Vol.31, No.1, Jan.-Feb. 1994, pp.138-145.10.2514/3.46466 Search in Google Scholar

[136] Hummel D., Oelker H., Effects of Canard Position on Aerodynamic Characteristics of a Close Coupled Canard Configuration at Low Speed, Z.Flugwiss. Weltraumforsch.15 (1991), pp.74-88. Search in Google Scholar

[137] Kendall E.R., Learjet G., The Minimum Induced Drag, Longitudinal Trim and Static Longitudinal Stability of Two Surface and Three Surface Airplanes, AIAA-84-2164. Search in Google Scholar

[138] Ericsson L., Cobra Maneuver Unsteady Aerodynamic Considerations, Jour.of Aircraft, Vol.32., No.1, pp.214-216.10.2514/3.46706 Search in Google Scholar

[139] Ransom S., Configuration Development of a Research Aircraft with Post Stall Manoeuvrability, J.Aircraft, Vol.20, No.7, July 1983, pp.599-605.10.2514/3.44917 Search in Google Scholar

[140] Gütter R., Friehmelt H., Haiplik R., Tactical Utility of the X 31A Using Post Stall Technologies, ICAS Proceedings, 96-3.7.5., pp.1574-1583, Sorento 1996. Search in Google Scholar

[141] Grafton S.B., Libbey Ch.E., Dynamic Stability Derivatives of a Twin Jet Fighter model for Angles of Attack from 10° to 110°, NASA TN D 6091, Washington Jan.1971. Search in Google Scholar

[142] Grafton S.B., Anglin E.L., Dynamic Stability Derivatives at Angle of Attack from -5° to 90° for the Variable Sweep Fighter Configuration with Twin Vertical Tails, NASA TN D-6909, Washington Oct.1972. Search in Google Scholar

[143] Goraj Z., High Angles Of Attack Flight Dynamics Of Contemporary And Prospective Fighters As A Function Of Their Configuration And Aerodynamics. Proceedings of 21^th Congress of the International Council of the Aeronautical Sciences, ICAS-98-1.7.5, 13-18 September 1998, Melbourne. Search in Google Scholar

[144] Fomin A., Su 27 Flanker Story. Air Fleet Russian Air Force, Aircraft & Space Review, Publisher: RA Intervestnik 2000. Search in Google Scholar

[145] Goraj Z., Aerodynamics & Dynamics of Manoeuvrable Aircraft with Elements of Computing, Scientific Series of Institute of Aviation, Vol.13, 473 pages, Warsaw 2001 (in Polish). Search in Google Scholar